Turbine engine component and method of cooling

ABSTRACT

A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

BACKGROUND

Turbine engines, and particularly gas or combustion turbine engines, arerotary engines that extract energy from a flow of pressurized combustedgases passing through the engine onto rotating turbine blades.

Turbine engines are often designed to operate at high temperatures toimprove engine efficiency. It is beneficial to provide cooling measuresfor components such as airfoils in the high-temperature environment,where such cooling measures can reduce material wear on these componentsand provide for increased structural stability during engine operation.

The cooling measures can include bleed air from the compressor that isrouted to the desired location in the engine. The bleed air can beutilized to provide purge air flow at specific component interfaces.Optimizing bleed air delivery and coverage further helps to improve theengine efficiency.

BRIEF DESCRIPTION

In one aspect, the disclosure relates to a component for a turbineengine including a body having an outer surface confronting a combustionair flow path and defining an interior, a first cooling passage havingat least a portion supplying cooling air to the interior of the body, asecond cooling passage having at least a portion supplying cooling airto the interior of the body and fluidly separated from the first coolingpassage, a scavenge passage fluidly separated from the second coolingpassage, and a first cyclone separator having a cooling air inlet, aclean air outlet fluidly coupled to the first cooling passage, and adirty air outlet fluidly coupled to the scavenge passage.

In another aspect, the disclosure relates to a component for a turbineengine including an airfoil body with an outer wall bounding an interiorand extending axially between a leading edge and a trailing edge todefine a chord-wise direction, and also extending between a root and atip to define a span-wise direction, a first cooling passage having atleast a portion supplying cooling air to the interior of the airfoilbody, a second cooling passage having at least a portion supplyingcooling air to the interior of the airfoil body and fluidly separatedfrom the first cooling passage, a scavenge passage, and a cycloneseparator having a cooling air inlet, a clean air outlet fluidly coupledto the second cooling passage, and a dirty air outlet fluidly coupled tothe scavenge passage.

In yet another aspect, the disclosure relates to a method of cooling acomponent in a turbine engine. The method includes flowing a supply ofcooling air to the component, directing a first portion of the supply ofcooling air to a cyclone separator located within the component to cleanthe first portion of the supply of cooling air, flowing the cleanedfirst portion through a first supply conduit to a cooling passage withinthe component, and flowing a second portion of the supply of cooling airthrough a second supply conduit to the cooling passage, the secondsupply conduit being fluidly separated from the cyclone separator.

BRIEF DESCRIPTION OF THE DRAWINGS

In the drawings:

FIG. 1 is a schematic cross-sectional diagram of a turbine engine for anaircraft.

FIG. 2 is a schematic side view of one component in the turbine engineof FIG. 1 in the form of a vane assembly according to various aspectsdescribed herein.

FIG. 3 is a schematic side view of the vane assembly of FIG. 2 includingair cooling passages and a cyclone separator for removing particles fromthe cooling air.

FIG. 4 is a cross-sectional view of the vane assembly of FIG. 2illustrating the interconnection of the cooling passages and the cycloneseparator.

FIG. 5 is a schematic side view of another component of the turbineengine of FIG. 1 in the form of a vane assembly having at least onecyclone separator according to various aspects described herein.

FIG. 6 is a schematic top view of another component of the turbineengine of FIG. 1 in the form of another vane assembly having a band withmultiple cyclone separators.

FIG. 7 is a schematic side view of another component of the turbineengine of FIG. 1 in the form of another vane assembly having a bafflewith a cyclone separator.

FIG. 8 is a schematic side view of another component of the turbineengine of FIG. 1 in the form of a sealing ring with a cyclone separator.

FIG. 9 is a schematic side view of another component of the turbineengine of FIG. 1 in the form of a nozzle support structure.

FIG. 10 is a schematic side view of another component of the turbineengine of FIG. 1 including a cyclone separator with a dedicated hanger.

DETAILED DESCRIPTION

The described embodiments of the present disclosure are directed towardcooled components within a turbine engine. For purposes of illustration,the present disclosure will be described with respect to the turbinesection in an aircraft turbine engine. It will be understood, however,that the disclosure is not so limited and may have general applicabilitywithin an engine, including in a compressor section, as well as innon-aircraft applications, such as other mobile applications andnon-mobile industrial, commercial, and residential applications.

Cooling airflows within turbine engines can carry dust or other debristhat can move into cooled components such as shrouds, hangers, airfoils,platforms, inner or outer bands, or the like. Such dust or debris cancollect within the interior of cooled components or cause blockageswithin cooling holes or passages. The removal of such debris can improvecooling performance and provide for reduced usage of cooling air.

Turbine engines can also include components formed by additivemanufacturing. As used herein, an “additively manufactured” componentwill refer to a component formed by an additive manufacturing (AM)process, wherein the component is built layer-by-layer by successivedeposition of material. AM is an appropriate name to describe thetechnologies that build 3D objects by adding layer-upon-layer ofmaterial, whether the material is plastic or metal. AM technologies canutilize a computer, 3D modeling software (Computer Aided Design or CAD),machine equipment, and layering material. Once a CAD sketch is produced,the AM equipment can read in data from the CAD file and lay down or addsuccessive layers of liquid, powder, sheet material or other material,in a layer-upon-layer fashion to fabricate a 3D object. It should beunderstood that the term “additive manufacturing” encompasses manytechnologies including subsets like 3D Printing, Rapid Prototyping (RP),Direct Digital Manufacturing (DDM), layered manufacturing and additivefabrication. Non-limiting examples of additive manufacturing that can beutilized to form an additively-manufactured component include powder bedfusion, vat photopolymerization, binder jetting, material extrusion,directed energy deposition, material jetting, sheet lamination, orceramic layering or stacking.

As used herein, the term “forward” or “upstream” refers to moving in adirection toward the engine inlet, or a component being relativelycloser to the engine inlet as compared to another component. The term“aft” or “downstream” used in conjunction with “forward” or “upstream”refers to a direction toward the rear or outlet of the engine or beingrelatively closer to the engine outlet as compared to another component.

As used herein, “a set” can include any number of the respectivelydescribed elements, including only one element. Additionally, the terms“radial” or “radially” as used herein refer to a dimension extendingbetween a center longitudinal axis of the engine and an outer enginecircumference.

All directional references (e.g., radial, axial, proximal, distal,upper, lower, upward, downward, left, right, lateral, front, back, top,bottom, above, below, vertical, horizontal, clockwise, counterclockwise,upstream, downstream, forward, aft, etc.) are only used foridentification purposes to aid the reader's understanding of the presentdisclosure, and do not create limitations, particularly as to theposition, orientation, or use of the disclosure. Connection references(e.g., attached, coupled, connected, and joined) are to be construedbroadly and can include intermediate members between a collection ofelements and relative movement between elements unless otherwiseindicated. As such, connection references do not necessarily infer thattwo elements are directly connected and in fixed relation to oneanother. The exemplary drawings are for purposes of illustration onlyand the dimensions, positions, order and relative sizes reflected in thedrawings attached hereto can vary.

FIG. 1 is a schematic cross-sectional diagram of a gas turbine engine 10for an aircraft. The engine 10 has a generally longitudinally extendingaxis or centerline 12 extending forward 14 to aft 16. The engine 10includes, in downstream serial flow relationship, a fan section 18including a fan 20, a compressor section 22 including a booster or lowpressure (LP) compressor 24 and a high pressure (HP) compressor 26, acombustion section 28 including a combustor 30, a turbine section 32including a HP turbine 34, and a LP turbine 36, and an exhaust section38.

The fan section 18 includes a fan casing 40 surrounding the fan 20. Thefan 20 includes a plurality of fan blades 42 disposed radially about thecenterline 12. The HP compressor 26, the combustor 30, and the HPturbine 34 form a core 44 of the engine 10, which generates combustiongases. The core 44 is surrounded by core casing 46, which can be coupledwith the fan casing 40. An annulus 95 can be defined between the core 44and the core casing 46.

A HP shaft or spool 48 disposed coaxially about the centerline 12 of theengine 10 drivingly connects the HP turbine 34 to the HP compressor 26.ALP shaft or spool 50, which is disposed coaxially about the centerline12 of the engine 10 within the larger diameter annular HP spool 48,drivingly connects the LP turbine 36 to the LP compressor 24 and fan 20.The spools 48, 50 are rotatable about the engine centerline and coupleto a plurality of rotatable elements, which can collectively define arotor 51.

The LP compressor 24 and the HP compressor 26 respectively include aplurality of compressor stages 52, 54 having blade assemblies 55 andvane assemblies 57. Each blade assembly 55 includes a set of compressorblades 56, 58 that rotate relative to each vane assembly 57 having acorresponding set of static compressor vanes 60, 62 (also called anozzle) to compress or pressurize the stream of fluid passing throughthe stage. In a single compressor stage 52, 54, multiple compressorblades 56, 58 can be provided in a ring and can extend radiallyoutwardly relative to the centerline 12, from a blade platform to ablade tip, while the corresponding static compressor vanes 60, 62 arepositioned upstream of and adjacent to the rotating blades 56, 58. It isnoted that the number of blades, vanes, and compressor stages shown inFIG. 1 were selected for illustrative purposes only, and that othernumbers are possible.

The blades 56, 58 for a stage of the compressor can be mounted to (orintegral to) a disk 61, which is mounted to the corresponding one of theHP and LP spools 48, 50. The vanes 60, 62 for a stage of the compressorcan be mounted to the core casing 46 in a circumferential arrangement.

The HP turbine 34 and the LP turbine 36 respectively include a pluralityof turbine stages 64, 66, having blade assemblies 65 and vane assemblies67. Each blade assembly 65 includes a set of turbine blades 68, 70 thatrotate relative to each vane assembly 67 having a corresponding set ofstatic turbine vanes 72, 74 (also called a nozzle) to extract energyfrom the stream of fluid passing through the stage. In a single turbinestage 64, 66, multiple turbine blades 68, 70 can be provided in a ringand can extend radially outwardly relative to the centerline 12, from ablade platform to a blade tip, while the corresponding static turbinevanes 72, 74 are positioned upstream of and adjacent to the rotatingblades 68, 70. It is noted that the number of blades, vanes, and turbinestages shown in FIG. 1 were selected for illustrative purposes only, andthat other numbers are possible.

The blades 68, 70 for a stage of the turbine can be mounted to a disk71, which is mounted to the corresponding one of the HP and LP spools48, 50. The vanes 72, 74 for a stage of the compressor can be mounted tothe core casing 46 in a circumferential arrangement.

Complementary to the rotor portion, the stationary portions of theengine 10, such as the static vanes 60, 62, 72, 74 among the compressorand turbine section 22, 32 are also referred to individually orcollectively as a stator 63. As such, the stator 63 can refer to thecombination of non-rotating elements throughout the engine 10.

In operation, the airflow exiting the fan section 18 is split such thata portion of the airflow is channeled into the LP compressor 24, whichthen supplies pressurized air 76 to the HP compressor 26, which furtherpressurizes the air. The pressurized air 76 from the HP compressor 26 ismixed with fuel in the combustor 30 and ignited, thereby generatingcombustion gases. Some work is extracted from these gases by the HPturbine 34, which drives the HP compressor 26. The combustion gases aredischarged into the LP turbine 36, which extracts additional work todrive the LP compressor 24, and the exhaust gas is ultimately dischargedfrom the engine 10 via the exhaust section 38. The driving of the LPturbine 36 drives the LP spool 50 to rotate the fan 20 and the LPcompressor 24.

A portion of the pressurized airflow 76 can be drawn from the compressorsection 22 as bleed air 77. The bleed air 77 can be drawn from thepressurized airflow 76 and provided to engine components requiringcooling. For example, the bleed air 77 can flow along a cooling air flowpath 90 passing through at least one of the engine core 44 and casing46. The temperature of pressurized airflow 76 entering the combustor 30is significantly increased. As such, cooling provided by the bleed air77 is necessary for operating of such engine components in theheightened temperature environments.

A remaining portion of the airflow 78 bypasses the LP compressor 24 andengine core 44 and exits the engine assembly 10 through a stationaryvane row, and more particularly an outlet guide vane assembly 80,comprising a plurality of airfoil guide vanes 82, at the fan exhaustside 84. More specifically, a circumferential row of radially extendingairfoil guide vanes 82 are utilized adjacent the fan section 18 to exertsome directional control of the airflow 78.

Some of the air supplied by the fan 20 can bypass the engine core 44 andbe used for cooling of portions, especially hot portions, of the engine10, and/or used to cool or power other aspects of the aircraft. In thecontext of a turbine engine, the hot portions of the engine are normallydownstream of the combustor 30, especially the turbine section 32, withthe HP turbine 34 being the hottest portion as it is directly downstreamof the combustion section 28. Other sources of cooling fluid can be, butare not limited to, fluid discharged from the LP compressor 24 or the HPcompressor 26.

FIG. 2 illustrates one turbine engine component 100 in the form of thevane assembly 67, such as that found in the HP turbine 34 (FIG. 1). Itwill be understood that aspects of the disclosure can be applied toother turbine engine components in other areas of the engine 10,including the turbine section 32 and compressor section 22, and alsoincluding the exemplary blade and vane assemblies 55, 57 or exemplaryblade assemblies 65 (FIG. 1), or any airfoil assembly within the turbineengine 10.

The vane assembly 67 includes the HP turbine vane 72 (also referred toas “vane 72”) and can form a nozzle in the HP turbine 34. The vane 72can include an airfoil body 101 having an outer wall 102 bounding aninterior 103 and having a pressure side 102P and a suction side 102S,extending axially between a leading edge 104 and a trailing edge 105 todefine a chord-wise direction, and also extending between a root 106 anda tip 107 to define a span-wise direction as shown.

The vane 72 extends from an inner band 108 to an outer band 109, wherethe root 106 is coupled to the inner band 108 and the tip 107 is coupledto the outer band 109. The inner bands 108 can also couple to the corecasing 46 (FIG. 1) and at least partially form the rotor 51. The body101 of the vane 72 can confront a combustion air flow path 99 which isillustrated by an arrow indicating a combustion flow direction.

At least one cyclone separator 140 can be included in the turbine enginecomponent 100. The cyclone separator 140 is shown as being includedwithin the outer band 109, and it should be understood that the cycloneseparator 140 can also be located within the inner band 108 or elsewherewithin the component 100 as desired. In a non-limiting example where thecomponent 100 is formed by additive manufacturing, it is contemplatedthat the component 100 can include a monolithic body having the vane 72,outer band 109, and cyclone separator 140. In such an example, thecomponent 100 can be formed in a single piece with an integrated cycloneseparator 140, vane 72, and outer band 109.

The core casing 46 can further include a frame 110, shown in dashedline, and a hanger 111. The component 100 can be mounted to the frame110 via the hanger 111, such as by coupling the outer band 109 to thehanger 111. In one example, the outer band 109 can include an integratedhanger in a unitary body. In an alternate example, the outer band 109can be mounted to a separate hanger 111. It should be understood thatthe core casing 46, including the frame 110 or hanger 111, can includeother components not shown in FIG. 2, such as an impingement baffle,film holes, seals, or structural connections, in non-limiting examples.

The cooling air flow path 90 is illustrated through the annulus 95. Inone example, the frame 110 and hanger 111 can define an interstitialspace 117 that at least partially forms the cooling air flow path 90 asshown. In this manner, the vane assembly 67 can be secured or mountedwithin the HP turbine 34, and the annulus 95 can be at least partiallydefined between the outer band 109 and core casing 46.

The component 100 can include a first cooling passage 122, a fluid inlet123, a second cooling passage 126, and a second fluid inlet 127. In theexample shown, the first and second cooling passages 122, 126 extendthrough the outer band 109 and vane 72. The fluid inlet 123 can be inthe form of a plenum, cavity, or fluid passage, and is fluidly coupledto the first cooling passage 122. The first and second cooling passages122, 126 can each be coupled to a supply of cooling air. In one examplethe cooling passages 122, 126 can be fluidly coupled to the same supplyof cooling air; in an alternate example, the cooling passages 122, 126can be fluidly coupled to independent or fluidly separated supplies ofcooling air. Either or both of the first and second cooling passages122, 126 can be fluidly coupled to the annulus 95 between the corecasing 46 and core 44 (FIG. 1). In the example shown, an inlet conduit120 fluidly couples the cooling air flow path 90 and the cycloneseparator 140, and the first cooling passage 122 can be fluidly coupledto the cyclone separator 140 via the fluid inlet 123. In this manner thecomponent 100 (e.g. the vane assembly 67) can be fluidly coupled to thecooling air flow path 90.

It should be understood a plurality of components 100 can be includedwithin the engine. For example, a plurality of vane assemblies 67 can bearranged circumferentially about the engine centerline 12 (FIG. 1),where the corresponding outer bands 109 at least partially define theannulus 95, and the corresponding fluid inlets 123 are circumferentiallyspaced about the annulus 95.

Turning to FIG. 3, the vane assembly 67 is illustrated in furtherdetail. The interior 103 of the vane 72 can include an interior coolingpassage 130 fluidly coupled to the first and second cooling passages122, 126. In this manner, the first and second cooling passages 122, 126can have at least a portion supplying cooling air to the interior 103 ofthe body 101.

In addition, a portion 128 of the second cooling passage 126 can befluidly separated from a portion 124 of the first cooling passage 122within the outer band 109. The first and second cooling passages 122,126 can also be fluidly coupled at an intersection 132. In theillustrated example, the intersection 132 is located within the interior103 of the vane 72 downstream of the cyclone separator 140. It should beunderstood that the first cooling passage 122, second cooling passage126, and intersection 132 can be located anywhere within the outer band109 and vane 72. In addition, either or both of the cooling passages122, 126 can furcate or branch upstream or downstream of theintersection 132. In one example (not shown), the first cooling passage122 can have a branch fluidly coupled to a first group of cooling holesupstream of the intersection 132, while another cooling passage canfluidly couple the intersection 132 to a second group of cooling holesdownstream of the intersection 132. In another example (not shown), thesecond cooling passage 126 can have a branch upstream of theintersection 132 that is fluidly coupled to a benign region within theairfoil. In still another example (not shown), each of the first andsecond cooling passages 122, 126 can include a branch upstream of theintersection 132 and fluidly coupled to respective first and secondgroups of cooling holes, and an additional cooling passage downstream ofthe intersection 132 can fluidly couple the intersection 132 to a thirdgroup of cooling holes. Such examples are given for illustrativepurposes and do not limit the disclosure.

A scavenge passage 134 can be fluidly coupled to the cyclone separator140 to direct a debris-laden airflow out of the component 100. It iscontemplated that the scavenge passage 134 can be fluidly coupled to abenign region 156. As used herein, a “benign region” will refer to aregion of the turbine engine 10 that is not adversely affected by thepresence of dust or debris, or has a sufficient tolerance to thepresence of dust or debris such that performance or efficiency of theturbine engine 10 is not reduced by an undesirable amount. For example,some regions within the engine 10 such as an upstream or downstreampurge cavity can be cooled or prevented from ingesting hot combustiongas flows by the use of cooling air, even as debris may be presentwithin the cooling air. “Benign region” can also refer to a region ofthe turbine engine 10 that is easily accessed or cleaned such that anyaccumulated dust or debris can be easily removed.

FIG. 4 illustrates a sectional view of the vane assembly 67 and cycloneseparator 140, where the second cooling passage 126 is illustrated inphantom within the outer band 109 for clarity. The cyclone separator 140includes a separator body 143 with a tangential cooling air inlet 144, aclean air outlet 145, and a dirty air outlet 146 (also referred to as“scavenge outlet” 146). In the illustrated example the cooling air inlet144, clean air outlet 145, and dirty air outlet 146 can be fluidlycoupled to the inlet conduit 120, first cooling passage 122, andscavenge passage 134, respectively.

The cyclone separator body 143 can include a conical portion 143Cadjacent the dirty air outlet 146, and an annular clean air conduit 148can be positioned within the cyclone separator 140 adjacent the coolingair inlet 144 and clean air outlet 145. An exemplary airflow 150 fromthe cooling air flow path 90 (FIG. 3) is shown entering the cycloneseparator 140 via the tangential cooling air inlet 144 and swirlingabout the clean air conduit 148. The airflow 150 is directed to theconical portion 143C and can accelerate due to the sloped sidewalls ofthe conical portion 143C. A first portion 151 of the airflow 150 isredirected back through the clean air conduit 148 and exits via theclean air outlet 145, while a second portion 152 of the airflow 150exits via the dirty air outlet 146 along with dirt and debris whosemomentum carries them out with the second portion 152. The secondportion 152 can define a debris-laden scavenge airflow 173 exiting thecyclone separator 140. In this manner a cooling circuit 160 can extendthrough the component 100 and be at least partially defined by thecooling air inlet 144 and the clean air outlet 145 of the cycloneseparator 140.

It should be understood that the first portion 151 of the airflow 150exiting the clean air outlet 145 can still carry some dirt or debris,wherein the majority of dirt or debris entering the cyclone separatorcan exit to the scavenge passage 134. Where a “cleaned” airflow or a“cleaned” portion of an airflow or air supply is described herein, itshould be understood that “cleaned” can refer to the removal of aportion less than the entirety of contaminants that may be present inthe airflow or air supply. “Cleaned” as used herein can also refer tothe removal of particles or contaminants larger than a predeterminedsize, such as the removal of particles larger than 1 micrometer from acooling air flow in one non-limiting example.

During operation, cooling air can be supplied to the component 100. Afirst portion 153 (FIGS. 3, 4) of the supply of cooling air can enterthe cyclone separator 140 to be cleaned as described above e.g. alongthe cooling air flow path 90 (FIG. 2), and the cleaned first portion 153can flow through the first supply conduit to the interior coolingpassage 130 within the vane 72. A second portion 154 (FIGS. 3, 4) of thesupply of cooling air can flow through a second supply conduit, such asthe second cooling passage 126, to the interior cooling passage 130. Thecleaned first portion 153 and the second portion 154 of the supply ofcooling air can be combined within the vane 72 at the intersection 132to cool the vane 72 with a reduced level of contaminants in the coolingair. In one non-limiting example of operation (not shown), cleanedcooling air from the cyclone separator 140 can be supplied via the firstcooling passage 122, or a branch thereof, to a group of cooling holes onthe pressure side 102P (FIG. 2). Dirty cooling air from the secondcooling passage 126 can be supplied to a benign region, or otherdust-tolerant region, within the vane or exhausted via a set of ejectionholes on the suction side 102S (FIG. 2). A mixture of cleaned air anddirty air can be formed at the intersection 132 and supplied to a thirdgroup of cooling holes, such as a set of trailing edge ejection holes.It will be understood that any or all of the cleaned first portion 153,non-cleaned second portion 154, or a mixture thereof, can be selectivelysupplied to any suitable region of the component 100.

Turning to FIG. 5, another component 200 is illustrated that can beutilized in the turbine engine 10. The component 200 is similar to thecomponent 100; therefore, like parts will be described with likenumerals increased by 100, with it being understood that the descriptionof the like parts of the component 100 applies to the component 200,except where noted.

The component 200 is illustrated as a vane assembly 167 with the HPturbine vane 72 extending between an inner band 208 and an outer band209. The combustion air flow path 99 is also shown and illustrates alocal combustion flow direction. It will be understood that aspects ofthe disclosure can be applied to other turbine engine components inother areas of the engine 10, including the turbine section 32 andcompressor section 22, and also including the exemplary blade and vaneassemblies 55, 57 or exemplary blade assemblies 65 (FIG. 1).

One difference is that a set of cyclone separators can be included in,or coupled to, either or both of the inner and outer bands 208, 209. Itis also contemplated that the set of cyclone separators can be arrangedin groups 225 of multiple cyclone separators. The groups 225 can includeany number of cyclone separators, including one, two, or more. Thecyclone separators can be provided or arranged in any suitableorientation within the inner or outer bands 208, 209.

A first exemplary configuration is illustrated in solid line where thegroup 225 includes an outer band cyclone separator 240A and an innerband cyclone separator 240B having corresponding dirty air outlets 246A,246B positioned upstream of corresponding clean air outlets 245A, 245Bwith respect to the local combustion air flow path 99. A secondexemplary configuration is illustrated in dashed line, where the group225 includes the outer and inner band cyclone separators 240A, 240Bhaving their corresponding dirty air outlets 246A, 246B positioneddownstream of their corresponding clean air outlets 245A, 245B. Each ofthe outer and inner band cyclone separators 240A, 240B can furtherinclude corresponding cooling air inlets 244A, 244B that can be suppliedwith cooling air for cleaning. In another example, both configurationscan be utilized for the same component 200 wherein two outer bandseparators 240A and two inner band separators 240B are provided in thevane assembly 167. In still another example (not shown), multiplecyclone separators can be provided and oriented within the outer band209 perpendicular to the combustion air flow path 99, with their cleanair outlets radially inward (or radially outward) of their dirty airoutlets. In this manner, at least some of the multiple cycloneseparators can be radially adjacent one of the outer or inner bands. Inaddition, at least some of the multiple cyclone separators can bepositioned between the outer band and the core casing 46.

The inner band 208 and outer band 209 can include a respective innerband cooling passage 212 and outer band cooling passage 214 supplyingcooling air to the interior 203 of the vane 72. Referring to the firstconfiguration (in solid line), the clean air outlet 245A of the outerband cyclone separator 240A can be fluidly coupled to the outer bandcooling passage 214, and the clean air outlet 245B of the inner bandcyclone separator 240B can be fluidly coupled to the inner band coolingpassage 216.

In operation, cooling air from the annulus 95 can flow through the firstand second cyclone separators 240A, 240B to define a cleaned firstsupply 271 of cooling air and a cleaned second supply 272 of coolingair. The cleaned first and second supplies 371, 372 can be directed intothe interior 203 of the component 200, such as via the inner or outerband cooling passage 212, 214 to at least one interior cooling passagewithin the vane 72.

FIG. 6 illustrates another component 300 similar to the components 100,200. Like parts will be described with like numerals further increasedby 100, with it being understood that the description of the like partsof the components 100, 200 applies to the component 300, except wherenoted.

The component 300 is illustrated as a vane assembly 267, similar to thevane assembly 167, with the HP turbine vane 72 extending between aninner band (not shown) and an outer band 309. The combustion air flowpath 99 is also shown and illustrates a local combustion flow direction.While shown and described with respect to the outer band 309, it will beunderstood that aspects of the disclosure can also be applied to aninner band in a vane assembly or to a platform in a blade assembly, innon-limiting examples. In addition, the component 300 can include othercomponents not shown, such as a baffle positioned between the outer bandand core casing. In addition, it will be understood that aspects of thedisclosure can be applied to other turbine engine components in otherareas of the engine 10, including the turbine section 32 and compressorsection 22, and also including the exemplary blade and vane assemblies55, 57 or exemplary blade assemblies 65 (FIG. 1).

It is contemplated that a set of cyclone separators 340 can be locatedin the turbine engine 10 within the annulus 95, such as between theouter band 309 and the core casing 46, or radially adjacent one of theinner band or outer band 309. Each cyclone separator 340 in the set canhave a cooling air inlet 244 fluidly coupled to the cooling air flowpath 90 (FIG. 1), a clean air outlet 345, and a scavenge outlet or dirtyair outlet 346 fluidly coupled to the cooling air flow path 90. In theillustrated example, the outer band 309 includes a first cycloneseparator 340A and a second cyclone separator 340B. Each of the cycloneseparators 340A, 340B have corresponding first and second cooling airinlets 344A, 344B, first and second clean air outlets 345A, 345B, andfirst and second dirty air outlets 346A, 346B.

The first and second cyclone separators 340A, 340B can have any desiredarrangement adjacent the outer band 309. Non-limiting examples ofarrangements include having each corresponding clean air outletdownstream of each corresponding dirty air outlet, or having theseparator body oriented perpendicular to the local combustion air flowpath 99. In this manner a cooling circuit 360 can extend through thecomponent 300 and be at least partially defined by the cooling air inlet344 and the clean air outlet 345 of the first cyclone separator 341.

It is also contemplated that the set of cyclone separators can includegroups 325 of at least two cyclone separators. The groups 325 caninclude any number of cyclone separators, including two, three, four, ormore. In addition, a common cooling air inlet 323 can be fluidly coupledto the at least two cyclone separators in the group 325. The commoncooling air inlet 323 is schematically represented in dashed line, andcan include a plenum, cavity, or fluid passage, in non-limitingexamples. The common cooling air inlet 323 is similar to the fluid inlet123 (FIG. 2) such that the common cooling air inlet 323 can be fluidlycoupled to the interior of the vane 72.

In the illustrated example, a group 325 includes the first and secondcyclone separators 340A, 340B provided side-by-side, circumferentiallylocated on opposite sides of the common fluid inlet 323, and coupled tothe outer band 309. The first and second clean air outlets 345A, 345Bare fluidly coupled to the common fluid inlet 323 and cooling passage349 which can extend through the outer band 309 and supply cleanedcooling air to the interior of an airfoil such as the vane 72. The firstand second dirty air outlets 346A, 346B each fluidly couple to scavengepassages 334 which supply a benign region 356 such as a downstream purgecavity.

In one example, it is contemplated that the plurality of airfoils andset of cyclone separators can be circumferentially arranged such that atleast one cyclone separator is positioned between circumferentiallyadjacent airfoils. In the example of FIG. 6, dashed lines schematicallyillustrate the position of circumferentially adjacent vanes 72 radiallyinward of, and coupled to, the outer band 309. The group 325 includingthe first and second cyclone separators 340A, 340B are positionedbetween the circumferentially adjacent vanes 72.

It should be understood that any number of cyclone separators can bepositioned between circumferentially adjacent airfoils in the engine 10,including one, two, or more. The cyclone separators positioned betweenadjacent airfoils can be of the same group. Alternately, cycloneseparators from different groups (e.g. having clean air outlets fluidlycoupled to different cooling passages) can be positioned betweenadjacent airfoils. Any number or arrangement of cyclone separators canbe utilized in the engine 10.

In operation, cooling air from the annulus 95 can flow through the firstand second cyclone separators 340A, 340B to define a cleaned firstsupply 371 of cooling air and a cleaned second supply 372 of coolingair. The cleaned first and second supplies 371, 372 can be combined atthe common cooling fluid inlet 323 and directed via the cooling passage349 to at least one interior cooling passage within the vane 72.

FIG. 7 illustrates another component 400 similar to the components 100,200, 300. Like parts will be described with like numerals furtherincreased by 100, with it being understood that the description of thelike parts of the components 100, 200, 300 applies to the component 400,except where noted.

The component 400 is illustrated as a vane assembly 367 similar to thevane assembly 67 with the vane 72 extending between an inner band 408and an outer band 409. The combustion air flow path 99 is also shown andillustrates a local combustion flow direction. For example, the vaneassembly 367 can at least partially form a stage-2 nozzle in the HPturbine 34 downstream of another vane assembly. In another non-limitingexample, the vane assembly 367 can at least partially form a stage-1nozzle upstream of all other nozzles in the HP turbine 34. In stillanother example, the component 400 can be located in any portion of thefan section 18, compressor section 22, or turbine section 32 as desired.

One difference is that a barrier wall 416 can be located within thecooling air flow path 90 (FIG. 1). The barrier wall 416 is shown in theform of a baffle 418 provided within or adjacent the outer band 409 toat least partially define an isolation chamber 435. It is contemplatedthat the isolation chamber 435 can be an annular isolation chamber.

In one example the baffle 418 can include perforations, such that theisolation chamber 435 can be partially fluidly sealed from the annulus95 via the perforated baffle 418. Alternately, the barrier wall 416 canbe configured to completely fluidly seal the isolation chamber 435, suchas by extending between or directly coupling the outer band 409 and thecore casing 46 (FIG. 2). In this manner, the barrier wall 416 cancooperate with at least one of the inner band 408 and outer band 409 tocollectively form at least part of the isolation chamber 435.

A cooling passage 422 can extend through the outer band 409 and fluidlycouple to the interior 403 of the vane 72. The cooling passage 422 canhave a fluid inlet 423 within or fluidly coupled to the isolationchamber 435. In the illustrated example, the vane 72 includes aninterior cooling passage 430 fluidly coupled to the cooling passage 422.

A cyclone separator 440 having a cooling air inlet 444, a clean airoutlet 445, and a dirty air outlet 446 can be provided, where the cleanair outlet 445 can be fluidly coupled to the isolation chamber 435. Inthe illustrated example, the cyclone separator 440 is mounted to thebaffle 418 and located within the isolation chamber 435. An inletconduit 420 can be fluidly coupled to the cooling air inlet 444 andextend outside of the isolation chamber 435. While one cyclone separator440 is shown, it is contemplated that multiple cyclone separators can belocated within the isolation chamber 435. In such a case, the multiplecyclone separators can be grouped to supply common fluid inlets asdescribed above, or can each supply an independent fluid inlet asdesired.

In operation, a dirty cooling airflow 470 can flow through the cycloneseparator 440. A cleaned cooling airflow 471 can be defined at the cleanair outlet 445, and a scavenge airflow 473 can be defined at the dirtyair outlet 446. The cleaned cooling airflow 471 can move into theisolation chamber 435 and be routed to other locations or components,such as blades, vane, shroud, hangers, or interior spaces thereof, innon-limiting examples. In one example, the cleaned cooling airflow 471can flow from the clean air outlet 445, through the isolation chamber435, and into the interior cooling passage 430 via the fluid inlet 423.In this manner, the interior cooling passage 430 can be fluidly coupledto the clean air outlet 445 of the cyclone separator 440. In addition,the scavenge airflow 473 can flow into a benign region 456 of theturbine engine 10.

FIG. 8 illustrates another component 500 similar to the components 100,200, 300, 400. Like parts will be described with like numerals furtherincreased by 100, with it being understood that the description of thelike parts of the components 100, 200, 300, 400 applies to the component500, except where noted.

The component 500 is illustrated as a sealing ring 47 attached to thecore casing 46. The cooling air flow path 90 (FIG. 1) can pass throughthe core casing 46 and core 44. A barrier wall 516 can be positionedbetween the core casing 46 and sealing ring 47 to at least partiallyform or define an isolation chamber 535 fluidly isolated from thecooling air flow path 90. The isolation chamber 535 can be an annularisolation chamber. In one example the barrier wall 516 can be in theform of a baffle 518, including a perforated baffle 518, such that theisolation chamber 535 is in partial fluid communication with the coolingair flow path 90. In another example, the barrier wall 516 can beconfigured to fully fluidly seal the isolation chamber 535.

A cyclone separator 540 having a cooling air inlet 544, a clean airoutlet 545, and a dirty air outlet 546 can be positioned within theisolation chamber 535. The cooling air inlet 544 can be fluidly coupledto the cooling air flow path 90 (FIG. 1), and the clean air outlet 545can be fluidly coupled to the isolation chamber 535.

In operation, a dirty cooling airflow 570 can flow through the cycloneseparator 540 and define a cleaned cooling airflow 571 at the clean airoutlet 545. The cleaned cooling airflow 571 can move into and becollected within the isolation chamber 535. Cleaned cooling air withinthe isolation chamber 535 can be routed to other locations or componentswithin the turbine engine as described above, such as via other passageswith inlets (not shown) fluidly coupled to the isolation chamber 535.

FIG. 9 illustrates another component 600 similar to the components 100,200, 300, 400, 500. Like parts will be described with like numeralsfurther increased by 100, with it being understood that the descriptionof the like parts of the components 100, 200, 300, 400, 500 applies tothe component 600, except where noted.

The component 600 is illustrated as a nozzle support 613 for a vaneassembly 667 similar to the vane assembly 67 (FIG. 2) and including anLP turbine vane 74. The nozzle support 613 includes an arm 615configured to mount a first portion 619 of the inner band 608 to therotor 51 (FIG. 1). An isolation chamber 635 can be formed by theplacement of a baffle 668 within the annulus 95 and positioned betweenthe arm 615 and a second portion 621 of the inner band 608. In theillustrated example, the baffle 668 includes perforations 669. Theisolation chamber 635 can be an annular isolation chamber, and can be atleast partially fluidly isolated from the annulus 95. In oneconfiguration shown in solid line, a cyclone separator 640 can bepositioned within the isolation chamber 635. A supply of dirty coolingair 670 exterior to the isolation chamber 635 can flow through theperforated baffle 668 and enter the cooling air inlet 644 of the cycloneseparator 640. Cleaned cooling air 671 can exit the clean air outlet 645and be collected within the isolation chamber 635. The cleaned coolingair 671 can be directed from the isolation chamber 635 to other regionsor components within the turbine engine 10, including the inner band 608or vane 74 in non-limiting examples. In one example, a band coolingpassage 622 can fluidly couple the isolation chamber 635 to an interiorcooling passage 630 within the vane 74. In addition, a scavenge airflow673 can exit the dirty air outlet 646 and be directed to a benign region656 as described above.

It is further contemplated that a second cyclone separator 640B, similarto the cyclone separator 640, can be positioned on the arm 615 of thenozzle support 613, outside of the isolation chamber 635. A supply ofdirty cooling air 670 can also enter the cyclone separator 640B via acooling air inlet 644B, and a dedicated cooling passage 675 can fluidlycouple the clean air outlet 645B to the isolation chamber 635. It iscontemplated in either configuration that a debris-laden scavengeairflow 673, 673B can be utilized in benign regions 656 such as purgecavities that are not sensitive to the presence of dust or debris. Inthis manner, multiple cyclone separators can be fluidly coupled to theisolation chamber 635, wherein a dirty cooling airflow can flow throughthe multiple cyclone separators and their cleaned cooling airflows canbe collected within a common isolation chamber.

FIG. 10 illustrates another component 700 similar to the components 100,200, 300, 400, 500, 600. Like parts will be described with like numeralsfurther increased by 100, with it being understood that the descriptionof the like parts of the components 100, 200, 300, 400, 500, 600 appliesto the component 700, except where noted.

The component 700 can be in the form of a vane assembly 767 defining astage 1 nozzle in the HP turbine 34 (FIG. 1), wherein a vane 72 extendsbetween an outer band 709 and an inner band (not shown). The outer band709 can form a portion of an annular turbine casing 33 that surroundsthe turbine section 32 (FIG. 1) radially inward of the core casing 46.

The combustor 30 is schematically illustrated upstream of the vaneassembly 767. An annular combustor casing 31 can be positioned upstreamof the vane assembly 767 and surround the combustor 30. The annulus 95can be at least partially defined between the combustor casing 31 andturbine casing 33.

A cyclone separator 740 with cooling air inlet 744, a clean air outlet745, and a dirty air outlet 746 can be included. One difference is thatthe cyclone separator 740 can be mounted to the core casing 46 on adedicated hanger 780. The hanger 780 can be secured to at least one ofthe combustor casing 31 and the turbine casing 33. In addition, thehanger 780 can at least partially define an isolation chamber 735 atleast partially fluidly isolated from the annulus 95. The isolationchamber 735 can be an annular isolation chamber. In the example of FIG.10, the hanger 780 is illustrated upstream of the outer band 709;however, any suitable location within the turbine engine 10 can beutilized. In one non-limiting example, the hanger 780 and isolationchamber 735 can be positioned between the HP compressor 26 (FIG. 1) andthe combustor 30 such that the combustor 30 is supplied with cleanedcooling air.

A cooling passage 722 can extend through the outer band 709 and fluidlycouple to an interior cooling passage 730 within the vane 72. Thecooling passage 722 can be fluidly coupled to the isolation chamber 735.During operation, a dirty cooling airflow 770 can enter the cooling airinlet 744 of the cyclone separator 740. A cleaned cooling airflow 771can exit the clean air outlet 745 and flow into the isolation chamber735. The cleaned cooling airflow 771 can also be directed from theisolation chamber 735 into the vane 72 via the cooling passage 722 andinterior cooling passage 730. In addition, a scavenge airflow 773 canexit the dirty air outlet 746 and be directed to a benign region 756,such as a space between adjacent airfoils or shroud segments innon-limiting examples.

It should be understood that aspects of the disclosure can be mixed andmatched. The below examples are given for illustrative purposes and arenot intended to be limiting.

In one example, two or more cyclone separators can have their clean airoutlets fluidly coupled to corresponding isolation chambers that arefluidly separated. In such a case, multiple cyclone separators can feedcleaned cooling air to separate chambers or plenums. In another example,multiple cyclone separators can be provided within a common isolationchamber, with their clean air outlets feeding the common isolationchamber. Alternately the multiple cyclone separators can have theirclean air outlets fluidly coupled to a common isolation chamber, whereat least some of the multiple cyclone separators are located outside ofthe common isolation chamber. In yet another example, each of multipleisolation chambers can be fed with cleaned cooling air from one or morecyclone separators, such as a first isolation chamber supplied withcleaned cooling air from two cyclone separators and a second isolationchamber supplied by a single cyclone separator.

In still another example, multiple chambers can be provided and fluidlycoupled, and at least one cyclone separator can provide cleaned coolingair to one of the multiple chambers. In such a case, the cleaned coolingair can flow through all of the fluidly-coupled chambers, which cansupply the cooling air to various portions of the turbine enginecomponent.

Aspects of the present disclosure provide for a method of cooling acomponent, such as the component 100, 200, 300, 400, 500, 600, 700 inthe turbine engine 10. The method includes flowing a supply of coolingair to the component. The method also includes directing a firstportion, such as the first portion 153 (FIG. 4) to a cyclone separator,such as the cyclone separator 140, 240, 340, 440, 540, 640 locatedwithin the component to clean the first portion of the supply of coolingair. The method further includes flowing the cleaned first portionthrough a first supply conduit, such as the clean air conduit 148, to acooling passage within the component such as the interior coolingpassage 130. The method further includes flowing a second portion, suchas the second portion 154, of the supply of cooling air through a secondsupply conduit to the interior cooling passage 130, wherein the secondsupply conduit is fluidly separated from the cyclone separator.Optionally, the method includes flowing a third portion of the supply ofcooling air to a second cyclone separator located within the componentto clean the third portion, and flowing the cleaned third portionthrough a third supply conduit to the interior cooling passage asdescribed in FIGS. 5 and 6. Optionally, the method can include combiningthe cleaned first portion and the cleaned third portion of the supply ofcooling air in the interior cooling passage as described in FIGS. 3-4.Optionally, the method can include flowing a dirty airflow from anoutlet of the cyclone separator such as the dirty air outlet 146 to anexterior portion of the component such as the benign region 156 via thescavenge passage 134 as described above. Optionally, the method caninclude combining the cleaned first portion and the second portion ofthe supply of cooling air in the cooling passage within the component asdescribed above.

Aspects additionally provide for another method of cooling a component,such as the component 100, 200, 300, 400, 500, 600, 700 in the turbineengine 10. The method can include flowing cooling air through a firstcyclone separator (e.g. the first cyclone separator 240A, 340A) locatedwithin the component to define a cleaned first supply 271, 371 ofcooling air, flowing cooling air through a second cyclone separator(e.g. the second cyclone separator 240B, 340B) located within thecomponent to define a cleaned second supply 272, 372 of cooling air, anddirecting the cleaned first and second supplies 271, 272, 371, 372 ofcooling air to at least one interior cooling passage within thecomponent. Optionally, the method can include combining the cleanedfirst and second supplies 271, 272, 371, 372 of cooling air within acommon conduit, such as the common fluid inlet 323, prior to thedirecting. Optionally, a first cyclone separator (e.g. the inner bandcyclone separator 240B) can be coupled to the inner band 208 and asecond cyclone separator (e.g. the outer band cyclone separator 240A)can be coupled to the outer band 209, with an airfoil (e.g. the vane 72)extending between the inner band 208 and outer band 209 as describedabove.

Aspects additionally provide for another method of cooling a component,such as the component 100, 200, 300, 400, 500, 600, 700 in the turbineengine 10. The method can include flowing a dirty cooling airflow via acooling air flow path through a cyclone separator, such as the cycloneseparator 140, 240, 340A, 340B, 440, 540, 640, 640B, 740, located withinan isolation chamber, such as the isolation chambers 435, 535, 635, atleast partially fluidly isolated from the cooling air flow path todefine a cleaned cooling airflow. The method also includes collectingthe cleaned cooling air within the isolation chamber via a clean airoutlet of the cyclone separator. The method can also include flowing thecleaned cooling airflow from the isolation chamber to an interior of thecomponent, such as the component 400 (FIG. 7). Optionally, thecollecting can further include collecting the cleaned cooling airflowwithin the isolation chamber at least partially defined by a baffle,which can include a perforated baffle such as that shown in FIG. 9.Optionally, the method can further include flowing the dirty coolingairflow through multiple cyclone separators each fluidly coupled to theisolation chamber via corresponding clean air outlets, such as thatshown in FIG. 9.

Aspects of the present disclosure provide for a variety of benefits,including an increase in component lifetime in engines that operate inhigh dust environments. It can be appreciated that the use of cyclonicseparators on individual turbine engine components can provide forcleaned cooling air without need of additional upstream separators orother debris removal components. Such removal of debris can improvecooling performance of the cooling air in and around the turbine enginecomponents. In addition, cooling air can be selectively cleaned forindividual components e.g. providing multiple cyclone separators for asingle component which may be more sensitive to the presence of dust,and providing a single cyclone separator for a more dust-tolerantturbine engine component. Improved cooling performance can provide forless cooling air supplied to the cooled components, improving engineefficiency during operation.

It can also be appreciated that grouping multiple cyclone separators tosupply common cooling air inlets can provide for simplified ductingwithin the engine, which lowers costs and improves process efficiencies,as well as providing for improved cooling for the engine component fromthe multiple cyclone separators.

In addition, the use of an isolation chamber to at least partiallycontain cleaned cooling air from the cyclone separators can provide forsimplified cooling structures, wherein multiple components can befluidly supplied to a common isolation chamber to receive the cleanedcooling air. Such simplification can reduce costs and improvemanufacturing efficiencies, as well as reducing an overall weight of theengine which improves engine efficiency.

It should be understood that application of the disclosed design is notlimited to turbine engines with fan and booster sections, but isapplicable to turbojets and turboshaft engines as well.

To the extent not already described, the different features andstructures of the various embodiments can be used in combination, or insubstitution with each other as desired. That one feature is notillustrated in all of the embodiments is not meant to be construed thatit cannot be so illustrated, but is done for brevity of description.Thus, the various features of the different embodiments can be mixed andmatched as desired to form new embodiments, whether or not the newembodiments are expressly described. All combinations or permutations offeatures described herein are covered by this disclosure.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they have structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal languages of the claims.

What is claimed is:
 1. A component for a turbine engine comprising: abody having an outer surface confronting a combustion air flow path anddefining an interior; a first cooling passage having at least a portionsupplying cooling air to the interior of the body; a second coolingpassage having at least a portion supplying cooling air to the interiorof the body and fluidly separated from the first cooling passage; ascavenge passage fluidly separated from the second cooling passage; anda first cyclone separator having a cooling air inlet, a clean air outletfluidly coupled to the first cooling passage, and a dirty air outletfluidly coupled to the scavenge passage.
 2. The component of claim 1wherein the scavenge passage supplies dirty cooling air to a benignregion of the turbine engine.
 3. The component of claim 1 wherein thebody further comprises a monolithic body having the outer surface, thefirst cooling passage, the second cooling passage, the scavenge passage,and the first cyclone separator.
 4. The component of claim 1 furthercomprising an intersection fluidly coupling the first cooling passageand the second cooling passage.
 5. The component of claim 4 wherein theintersection is positioned downstream of the first cyclone separator. 6.The component of claim 4 wherein the intersection is within the interiorof the body.
 7. The component of claim 6 further comprising an interiorcooling passage within the body fluidly coupled to the first and secondcooling passages via the intersection.
 8. The component of claim 1further comprising one of a nozzle support, a platform, an inner band,an outer band, a shroud, or a sealing ring.
 9. The component of claim 1further comprising a cooling circuit extending through the component andat least partially defined by the cooling air inlet and the clean airoutlet of the first cyclone separator.
 10. The component of claim 1wherein the dirty air outlet of the first cyclone separator is fluidlyseparated from the interior of the body.
 11. The component of claim 1further comprising a second cyclone separator having a clean air outletfluidly coupled to the interior of the body.
 12. The component of claim11 wherein the clean air outlet of the second cyclone separator isfluidly coupled to the clean air outlet of the first cyclone separator.13. A component for a turbine engine, comprising: an airfoil body withan outer wall bounding an interior and extending axially between aleading edge and a trailing edge to define a chord-wise direction, andalso extending between a root and a tip to define a span-wise direction;a first cooling passage having at least a portion supplying cooling airto the interior of the airfoil body; a second cooling passage having atleast a portion supplying cooling air to the interior of the airfoilbody and fluidly separated from the first cooling passage; a scavengepassage; and a cyclone separator having a cooling air inlet, a clean airoutlet fluidly coupled to the second cooling passage, and a dirty airoutlet fluidly coupled to the scavenge passage.
 14. The component ofclaim 13 wherein the airfoil body comprises a vane extending from aninner band to an outer band, and wherein a first cyclone separator islocated within one of the inner band or the outer band.
 15. Thecomponent of claim 14 further comprising a second cyclone separatorlocated within the other of the inner band or the outer band and havinga second clean air outlet fluidly coupled to the interior of the airfoilbody.
 16. A method of cooling a component in a turbine engine, themethod comprising: flowing a supply of cooling air to the component;directing a first portion of the supply of cooling air to a cycloneseparator located within the component to clean the first portion of thesupply of cooling air; flowing the cleaned first portion through a firstsupply conduit to a cooling passage within the component; and flowing asecond portion of the supply of cooling air through a second supplyconduit to the cooling passage, the second supply conduit being fluidlyseparated from the cyclone separator.
 17. The method of claim 16 furthercomprising flowing a third portion of the supply of cooling air to asecond cyclone separator located within the component to clean the thirdportion, and flowing the cleaned third portion through a third supplyconduit to the cooling passage.
 18. The method of claim 17 furthercomprising combining the cleaned first portion and the cleaned thirdportion of the supply of cooling air in the cooling passage within thecomponent.
 19. The method of claim 16 further comprising flowing a dirtyairflow from an outlet of the cyclone separator to an exterior portionof the component via a scavenge passage.
 20. The method of claim 16further comprising combining the cleaned first portion and the secondportion of the supply of cooling air in the cooling passage within thecomponent.